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E. Install the lower torsion link.
S 414-045
(1)
Apply grease to, and install, the parts that follow to connect the lower torsion link (5) to the shock strut (View A-A):
(a)
Pin (6)
(b)
Lockbolt (7)
(c)
Washer (8)
(d)
Nut (9) 1) Tighten the nut to 150-200 pound-inches.
NOTE: If necessary, you can loosen the nut to the
____ nearest lock position to install the cotter pin.
(e) Cotter Pin
S 424-047
(2)
Apply grease to, then install, these parts to connect the upper torsion link (11) to the lower torsion link (5) (View B-B):
(a)
Apex Pin (12)
(b)
Washer (13, 14, and 16)
(c)
Nut (15) 1) Tighten the nut to 200-250 pound-inches.
(d)
Cotter Pin
F.
Put the Airplane Back to Its Usual Condition.
S 414-051
(1)
Install the wheel and the tire on the nose landing gear
(AMM 32-45-02/401).
S 584-052
(2)
Lower the axle of the nose landing gear and remove the axle jack (AMM 07-11-03/201).
S 864-065
(3)
Remove the DO-NOT-OPERATE tags from the control lever for the landing gear. Put the lever on the DN position.
(4)
Lubricate the torsion link at the grease fittings.
S 644-054
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S 824-119
(5)
Do this task "Measure/Adjust the Clearance for the Nose Landing Gear Not Compressed Sensor" (AMM 32-09-08/201), if you did one of the tasks that follow:
(a)
You replaced a torsion link bushing(s).
(b)
You installed a new upper/lower torsion link.
(c)
You installed a new sensor/target.
(d)
You moved or damaged the sensor/target bracket.
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NOSE GEAR TORSION LINKS - INSPECTION/CHECK
__________________________________________
1. General_______
A. This procedure only has an illustration, and a wear limit table which shows the data for wear limits. There are no procedures for access, removal, or installation of the parts. Refer to the Nose Gear Torsion Links - Removal/Installation for the procedure to do these tasks.
TASK 32-21-09-206-001
2. Wear Limits for the Torsion Links of the Main Landing Gear (Fig. 601)__________________________________________________________
A. Wear Limits for the Torsion Links
S 226-002
(1) Refer to Fig. 601 for the inspection points and the wear limits table.
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C-C
Nose Landing Gear Torsion Links Wear Limits
Figure 601 (Sheet 1)
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NO. INDEX PART NAME DIM. DESIGN LIMITS WEAR LIMITS WORN PART REPLACE PART WORN REPAIR INSTR REPAIR
DIAMETER PER-MITTED WEAR DIM. MAX ANCE CLEAR-DIAM
MIN MAX
1 BUSHING ID 1.5000 1.5010 1.5040 0.0050 X
PIN OD 1.4980 1.4990 1.4960 X 1
2 BUSHING ID 1.5000 1.5010 1.5044 0.0054 X
PIN OD 1.4980 1.4990 1.4956 X 1
3 BUSHING ID 0.3750 0.3790 0.3812 0.0047 X
BOLT OD 0.3735 0.3745 0.3723 X
4 SHOCK STRUT LOWER LINK/ 5.9330 5.9390 5.9770 2 0.0380 3
5 BUSHING ID 0.7500 0.7510 0.7537 0.0047 X
PIN OD 0.7480 0.7490 0.7463 X
6 APEX JOINT 1.6140 1.6180 1.6290 2 0.0110 3
7 BUSHING ID 1.2500 1.2510 1.2540 0.0050 X
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本文鏈接地址：757 AMM 飛機維護手冊 起落架 CHAPTER 32 - LANDING GEAR 2(3)
